Parachute deployment line and cut knife

ABSTRACT

A releasable deployment line for a parachute system is provided. The releasable deployment line may include a first segment of material including an aircraft end configured to be operably connected to an aircraft, and a release end configured to be operably connected to a first section of a multi-ring release system. The replaceable deployment line may further include a second segment of material including a container end configured to be operably connected to a parachute container, and a ring end configured to be operably connected to a second section of the multi-ring release system and a third segment of material. The third segment of material may include a parachute end configured to be operably connected to a parachute within the parachute container, and a pin end configured to be operably connected to a retaining pin associated with the first section of the multi-ring release system.

TECHNICAL FIELD

The present disclosure relates to parachute deployment systems. Moreparticularly, the disclosure relates to a parachute deployment line andrestraint release device associated with parachute deployment.

BACKGROUND INFORMATION

Air based cargo delivery systems (e.g., parachute based delivery) arefrequently used to drop cargo or persons from an aircraft and controldescent (e.g., speed) of the cargo such that the cargo may land safelyand be recovered by a ground team. To accomplish this task, an item ofcargo may be equipped with a parachute system, including a parachutecontainer, a parachute, a restraint release device (e.g., a cut-knife),and a static line connected to the parachute container and canopy, amongother things. This parachute system may initially be affixed to thecargo item via one or more lengths of restraint material (e.g., nyloncord) in preparation for transport to a desired location via anaircraft.

Prior to the cargo exiting the aircraft at altitude, one end of thestatic line may be connected to an anchor in the aircraft such that,upon exit of the cargo, tension may be applied to the static linecausing the restraint release device to release (e.g., cut) the segmentsof material affixing the parachute system to the cargo. Once thesesegments are cut, the static line may cause the parachute container tobe opened and the canopy to separate from the static line and parachutecontainer. The dangling static line and parachute container may then beretrieved and brought into the aircraft by aircraft personnel.

In some circumstances (e.g., high altitude delivery) it has beendesirable to utilize a “release away” or “breakaway” static line toeliminate the need for a crewman to retrieve the static line andparachute container from outside the aircraft. These release away staticlines may include a “U” connector between two segments of static line,and a locking loop configured to hold the U connector in place, amongother things. When tension is applied to such a static line, the forcerequired to release the U connector from the locking loop and achievethe “release away” may increase exponentially with the amount of tensionpresent in the static line. Twisting of the releasable static line alsomay further increase forces associated with release. Testing of somereleasable static lines has demonstrated that where 100 pounds oftension is applied to a straight releasable static line, 200 pounds offorce, or more, may be used to release the U connector.

Also adding to the forces associated with the releasable static line maybe a force associated with a restraint release device for releasing theparachute container from its pre-drop location. Prior art “cut-knives”used for such purposes may dull quickly (e.g., as a result of excessiveforce), resulting in additional force to cause the cutting of therestraint material. In some instances, it has been determined that inexcess of 400 pounds of force has been used to cut the restraintmaterial.

Large forces exerted on the releasable static line, such as from therelease-away and restraint release systems, may cause problems such asrecoil of the static line and subsequent damage to the aircraft,parachute system, and/or aircraft crew. Therefore, it may be desirableto limit the force necessary to cause the release away of a releasablestatic line associated with a parachute.

Further, previous restraint release devices have suffered from otherissues such as, their inability to be reused based on sharpeningdifficulties. Therefore, using and replacing such devices can may becomecost ineffective.

The present disclosure is directed to addressing one or more of thedesires and issues discussed above utilizing various examples of areleasable parachute deployment line and/or restraint release device.

Although the present invention may obviate one or more of theabove-mentioned needs, it should be understood that some aspects andembodiments of the invention might not necessarily obviate one or moreof those needs.

SUMMARY OF THE DISCLOSURE

In the following description, certain aspects and embodiments willbecome evident. It should be understood that the invention, in itsbroadest sense, could be practiced without having one or more featuresof these aspects and embodiments. It should also be understood thatthese aspects and embodiments are merely exemplary.

In one aspect, as embodied and broadly described herein, a releasabledeployment line for a parachute system is provided. The releasabledeployment line may include a first segment of material comprising anaircraft end configured to be operably connected to an aircraft, and arelease end configured to be operably connected to a first section of amulti-ring release system. The releasable deployment line may furtherinclude a second segment of material comprising a container endconfigured to be operably connected to a parachute container, and a ringend configured to be operably connected to a second section of themulti-ring release system, and a third segment of material comprising aparachute end configured to be operably connected to a parachute withinthe parachute container, and a pin end configured to be operablyconnected to a retaining pin associated with the first section of themulti-ring release system.

In another aspect, a restraint release device for a parachute system isprovided. The restraint release device may include a frame comprising afirst support member and a second support member, each of the firstmember and the second member further comprising an aperture configuredto receive at least one object. The restraint release device may furtherinclude two or more blades each comprising a cutting surface, whereinthe two or more blades are opposably mounted at a blade end associatedwith the frame, wherein the cutting surface of each of the two or moreblades is exposed within the aperture such that an acute angle betweenthe cutting surface of each of the two or more blades is formed withinthe aperture at the blade end, wherein the restraint release device isoperably connected to a deployment line associated with the parachutesystem.

In yet another aspect, a parachute deployment system is provided. Theparachute deployment system may include a first segment of materialcomprising an aircraft end configured to be operably connected to anaircraft, and a release end configured to be operably connected to afirst section of a multi-ring release system, and a second segment ofmaterial comprising a container end configured to be operably connectedto a parachute container, and a ring end configured to be operablyconnected to a second section of the multi-ring release system. Theparachute deployment system may further include a third segment ofmaterial comprising a parachute end configured to be operably connectedto a parachute within the parachute container, and a pin end configuredto be operably connected to a retaining pin associated with the firstsection of the multi-ring release system, wherein the retaining pin isconfigured to be slidably positioned within a retaining loop associatedwith the multi-ring release system, and a restraint release device. Therestraint release device may include a frame comprising a first supportmember and a second support member, each of the first member and thesecond member further comprising an aperture configured to receive atleast one object, and two or more blades each comprising a cuttingsurface. The two or more blades may be opposably mounted at a blade endassociated with the frame and with the cutting surface of each of thetwo or more blades exposed within the aperture such that an anglebetween the cutting surface of each of the two or more blades is formedwithin the aperture at the blade end. The restraint release device maybe operably connected to a deployment line associated with the parachutesystem.

In yet another aspect, a system is provided. The system may include acargo, a parachute operably connected to the cargo, and a releasabledeployment line operably connected to the parachute. The releasabledeployment line may include a first segment of material comprising anaircraft end configured to be operably connected to an aircraft, and arelease end configured to be operably connected to a first section of amulti-ring release system, and a second segment of material comprising acontainer end configured to be operably connected to a parachutecontainer, and a ring end configured to be operably connected to asecond section of the multi-ring release system. The releasabledeployment line may further include a third segment of materialcomprising a parachute end configured to be operably connected to aparachute within the parachute container, and a pin end configured to beoperably connected to a retaining pin associated with the first sectionof the multi-ring release system, wherein the retaining pin isconfigured to be slidably positioned within a retaining loop associatedwith the multi-ring release system. The system may further include arestraint release device operably connected to the releasable deploymentline. The restraint release device may include a frame comprising afirst support member and a second support member, each of the firstmember and the second member further comprising an aperture configuredto receive at least one object, and two or more blades each comprising acutting surface. The two or more blades may be opposably mounted at ablade end associated with the frame, and the cutting surface of each ofthe two or more blades may be exposed within the aperture such that anacute angle between the cutting surface of each of the two or moreblades is formed within the aperture at the blade end.

Aside from the structural arrangements set forth above, the inventioncould include a number of other arrangements, such as those explainedhereinafter. It is to be understood that both the foregoing descriptionand the following description are exemplary.

BRIEF DESCRIPTION OF THE FIGURES

The accompanying drawings, which are incorporated in and constitute apart of this specification, illustrate a number of non-limitingembodiments of the invention and together with the description, serve toexplain the principles of the invention.

FIG. 1 is an illustration of exemplary parachute and cargo systems,including an exemplary parachute deployment line;

FIG. 2 is an illustration of a front section of an exemplary breakawayparachute deployment line associated with the parachute and cargosystems;

FIG. 3 is an illustration of a rear section of the exemplary breakawayparachute deployment line shown in FIG. 2;

FIG. 4 is an illustration of a second segment of material associatedwith the exemplary parachute deployment line shown in FIG. 2, and anexemplary restraint release device;

FIG. 5A is a detailed illustration of the exemplary restraint releasedevice of FIG. 3;

FIG. 5B is an exploded detailed illustration of the exemplary restraintrelease device of FIG. 5A;

FIG. 6 is an illustration of yet another exemplary restraint releasedevice including a hinged opening; and

FIG. 7 is an exemplary flowchart illustrating a method for deployment ofan exemplary parachute and cargo system.

DETAILED DESCRIPTION

Reference will now be made in detail to the exemplary embodiments of theinvention, examples of which are illustrated in the accompanyingdrawings. Wherever possible, the same reference numbers will be usedthroughout the drawings to refer to the same or like parts. It is to beunderstood that both the foregoing general description and the followingdetailed description are exemplary and explanatory only and are notrestrictive of the invention, as claimed.

FIG. 1 is an illustration of an exemplary parachute and cargo system 1,including an exemplary parachute deployment line 8 and restraint releasedevice 40. Parachute and cargo systems may be utilized for deliveringcargo from an aircraft to a ground location while slowing descent, amongother things. Such systems may include static deployment lines, therebyenabling deployment of a parachute upon the system's exit from anaircraft (i.e., minimizing manual intervention). Cargo 2 may beassociated with a parachute container 3 containing a parachute (notshown). Parachute container 3 may be secured to cargo 2 via restraints 4to substantially maintain contact between parachute container 3 andcargo 2 until exit from an aircraft. Parachute deployment line 8 maythen provide an operable connection between an aircraft (not shown),parachute container 3, parachute (not shown), and restraint releasedevice 40, among other things.

FIG. 2 is an illustration of a front section of an exemplary parachutedeployment line 8 configured to breakaway upon deployment of theparachute. Parachute deployment line 8 may include a first segment ofmaterial 10, a second segment of material 12, a third segment ofmaterial 26, and a multi-ring release system 16.

First segment of material 10 may be configured to participate in staticline deployment of a parachute associated with parachute and cargosystem 1. First segment of material 10 may include an operableconnection between an aircraft and multi-ring release system 16, andultimately an operable connection to the parachute via second segment ofmaterial 12. First segment of material 10 may be comprised of a materialwith a desired strength for tolerating loads and stresses related to thedeployment of parachute and cargo system 1. Such materials may include,for example, braided nylon, nylon webbing, polyester webbing, cottonwebbing, and any other suitable material. The materials used may be sewnor otherwise fabricated into a design or shape such that a desired shapeand strength may be obtained.

First segment of material 10 further may include an aircraft end 114configured to be operably connected to an aircraft, and a release end116 configured to be operably connected to a first section of amulti-ring release system 16. Aircraft end 114 may include a connectingdevice 14 configured to be operably affixed to an anchor (e.g., ananchor cable, hook, or other suitable device) associated with anaircraft. For example, connecting device 14 may include a clevis 14, pin21, and cotter 22 configuration. In such a configuration, an anchorassociated with an aircraft may be placed in the opening of clevis 14and pin 21 inserted through clevis 14 to secure clevis 14 to the anchor.Cotter 22 may then be used to secure pin 21 within clevis 14.Alternatively, other configurations may be used for connecting device14, such as, for example, a carabineer type connector, or any othersuitable configuration allowing connection and disconnection of aircraftend 114 of first segment of material 10, to/from an anchor associatedwith an aircraft.

Release end 116 of first segment of material 10 may include an operableconnection to a first section of multi-ring release system 16.Multi-ring release system 16 may be configured to allow first segment ofmaterial 10 to breakaway from second segment of material 12 followingdeployment of a parachute. A first section of multi-ring release system16 may include a first ring 19, a second ring 20, and possibly also asmany additional rings as desired. Although multi-ring release system 16will be described in the context of a three-ring system in thisdescription, more or fewer rings may be used as desired. For example, amulti-ring release system may include three, four, five, six, or morerings, depending on numerous factors such as potential load and lengthof parachute deployment line 8, among other things. Further, any ordinalidentifier (e.g., first, second, etc.) used throughout thisspecification to reference a ring associated with multi-ring releasesystem 16 is intended to be exemplary only and not to denote absoluteorder of rings or number of rings present in multi-ring release system16. As noted, more or fewer rings may be utilized and any suitablenatural number may be used to reference a ring in multi-ring releasesystem 16. Moreover, rings associated with multi-ring release system 16may not be limited to an annular shape and may be of any size and shapeas desired.

First ring 19, second ring 20, as well as any additional rings, may beoperably connected to first segment of material 10 using, for example,looped fabric, fasteners, eyelets, or other suitable fasteningmechanisms. In one example, webbed nylon loops may be affixed (e.g.,sewn, riveted, etc.) to first segment of material 10 with first ring 19and second ring 20 passing through the openings created by the loops, asshown. This may allow at least some force exerted on each of first ring19 and second ring 20—and any additional rings affixed to first segmentof material 10 in a similar manner—to be transferred to first segment ofmaterial 10, and ultimately to an anchor device within an aircraft.

Load ring 18 may be operably connected to a ring end 112 of secondsegment of material 12. Both second segment of material 12 and load ring18 may be configured to support a load associated with cargo 2 or anyother item attached to a deployment end 110 of parachute deployment line8 (e.g., a skydiver). Such a connection may be achieved using one ormore types of connector structures such as, for example, fabric loops,grommets and fasteners, or any other suitable method. Load ring 18 maybe of any desired diameter, and in one example, may be sized based onthe load to be attached. Further, load ring 18 may include any materialsuitable for supporting an associated load.

Based on such a configuration, second ring 20 may be passed through loadring 18, and first ring 19 passed through second ring 20, with each ringpivoting to restrain the ring before it. First ring 19 may berestrained, as shown, by a cord section 17 configured to pass over firstring 19 and through first segment of material 10 (e.g., through agrommet). Cord section 17 may include a loop through which a retainingpin (shown in FIG. 3) may be passed, thereby substantially preventingcord section 17 from releasing first ring 19 until retaining pin 24 isslidably removed.

FIG. 3 is an illustration of a rear section of an exemplary breakawayparachute deployment line 8 highlighting a method for restraining firstring 19, and upon assembly of multi-ring release system 16, all rings ofmulti-ring release system 16. Retaining pin 24 may include a cotter orother similar pin with a length greater than the width of the opening infirst segment of material 10 through which cord section 17 is configuredto pass. Retaining pin 24 may further include safety devices (e.g.,safety ties) to minimize the likelihood of removal prior to a desiredremoval time.

Retaining pin 24 may be operably connected to a pin end of third segmentof material 26 such that, upon a force being exerted on third segment ofmaterial 26, retaining pin 24 may be slidably extracted from cordsection 17, thereby allowing first ring 19 to move freely about itsconnection to first segment of material 10. This may, in turn, alloweach ring of multi-ring release system 16 to cascade free from itsrestraining ring, resulting in separation of load ring 18 frommulti-ring release system 16 and disconnection of first segment ofmaterial 10 from second segment of material 12.

Second segment of material 12 may include an operable connection betweenmulti-ring release system 16, a parachute container 3, and ultimately anaircraft via first segment of material 10. Second segment of material 12may include a ring end 112, configured to be operably connected to loadring 18 and subsequently to multi-ring release system 16 (e.g., loadring 18), and a deployment end 110. Second segment of material 12 may becomprised of a material with a desired strength for tolerating loads andstresses related to the deployment of a parachute system and associatedcargo. Such materials may include, for example, braided nylon, nylonwebbing, cotton webbing, and any other suitable material. The materialsused may be sewn or otherwise fabricated into a design or shape suchthat a desired shape and strength may be obtained.

Deployment end 110 may be configured to provide an operable connectionbetween an aircraft and parachute container 3. Deployment end 110 mayinclude a device enabling operation of an opening mechanism associatedwith parachute container 3. For example, deployment end 110 may includea length of material associated with second segment of material 12looped back and affixed onto another area of second segment of material12. This may result in formation of a container loop 28, as shown inFIG. 3, associated with deployment end 110. In such a configuration,container loop 28 may be operably connected to an opening mechanismassociated with parachute container 3 such that, upon a force beingapplied to second segment of material 12 (e.g., upon deployment ofparachute system from an aircraft), container loop 28 may causeactuation of the opening mechanism associated with parachute container 3and subsequent deployment of the parachute (not shown).

As described above, ring end 112 of second segment of material 12 mayinclude an operable connection to load ring 18 associated withmulti-ring release system 16. Load ring 18 may be operably connected toring end 112 in any suitable manner. For example, material associatedwith ring end 112 may be looped back upon itself resulting in formationof a fabric loop. Load ring 18 may then be inserted inside the formedloop and the loop secured to second segment of material 12. One ofordinary skill in the art will recognize that numerous methods exist forsecuring load ring 18 to ring end 112. Any such method is intended tofall within the scope of the present disclosure.

Third segment of material 26 may be configured to provide an operableconnection between a parachute (not shown) and retaining pin 24, amongother things. Third segment of material 26 may be comprised of materialssuch as, for example, a cord or strap, having suitable strength forbearing loads associated with third segment of material 26. In oneexample, third segment of material 26 may include a nylon or polyestercord of a desired length, enabling a connection between parachute (notshown) and retaining pin 24. Further, third segment of material 26 maybe configured to pass slidably through a sleeve or pocket associatedwith second segment of material 12 to substantially prevent thirdsegment of material from becoming tangled or otherwise encumbered.

To facilitate an operable connection between parachute (not shown) andretaining pin 24, third segment of material 26 may include a canopy loop29 or other suitable connector associated with a parachute end and beconfigured to be operably connected to a parachute (not shown). Such acanopy loop 29 (or other device) may be connected to the parachute (notshown) prior to the parachute being packed into parachute container 3,or alternatively, the parachute may be connected to canopy loop 29 afterbeing packed into parachute container 3 (e.g., an extension line outsideof parachute container 3 may be used for the connection).

As noted above, a pin end associated with third segment of material 26may be operably connected to retaining pin 24. For example, retainingpin 24 may include a connection point (e.g., a hole or loop) such thatthe pin end may be tied, clipped, or otherwise affixed to retaining pin24. When a pulling force is applied to third segment of material 26 atparachute end, a force may be transferred to retaining pin 24, therebycausing retaining pin 24 to be slidably removed from cord section 17.For example, because third segment of material 26 may be of a finitelength, during descent of parachute system 1, parachute may eventuallyexert a pulling force on third segment of material 26. This force may besufficient to slidably extract retaining pin 24 from cord section 17such that multi-ring release system 16 is released and second segment ofmaterial 12 is allowed to breakaway from first segment of material 10.

FIG. 4 is a sectional illustration of a length of second segment ofmaterial 12 associated with an exemplary parachute deployment line 8 andan exemplary restraint release device 40. Restraint release device 40may be configured to cause a release (e.g., cutting) of parachuterestraints 4 upon deployment of parachute system 1 from an aircraft suchthat parachute container 3 may be removed from direct contact with cargo2. Cargo 2 may then subsequently remain connected to parachute container3—and parachute (not shown)—via straps, risers, or other suitableconnecting devices while descending.

Restraint release device 40 may be operably connected to parachutedeployment line 8 via a length of material 62 and release connector 60such that, upon deployment, forces exerted on parachute deployment line8 may be transferred to restraint release 40 via length of material 62.Length of material 62 may be comprised of any suitable materialconfigured to substantially withstand such forces and may be affixed atany desired location on parachute deployment line 8 (e.g., secondsegment of material 12).

FIG. 5A is a detailed illustration of an exemplary assembled restraintrelease device 40, and FIG. 5B shows an exemplary restraint releasedevice 40 in an exploded view. Restraint release device 40 may include aframe 44 having a first end 46 and a blade end 48, and two or moreblades 45 and 47. Frame 44 may be configured to provide support toblades 45 and 47. Frame 44 may include a first support member 41 and asecond support member 43 configured to be operably connected, which mayresult in formation of a substantially single entity associated withframe 44. First support member 41 and second support member 43 may be ofsubstantially the same size and shape and, in one example, each of firstsupport member 41 and second support member 43 may be of a substantiallyoval or oblong shape and may taper from a first end 46 to a blade end48. Further, first support member 41 and second support member 43 mayinclude one or more fastening points 50 configured to receive fasteners49 for purposes of operably connecting together first support member 41and second support member 43, among other things. Fastening points 50associated with first support member 41 may be substantially alignedwith fastening points 50 associated with second support member 43, thusenabling fastening by fasteners 49. One of ordinary skill in the artwill recognize that first support member 41 and second support member 43may be of any suitable size and shape (e.g., a trapezoid) withoutdeparting from the scope of the present disclosure.

Each of first support member 41 and second support member 43 may befabricated or otherwise manufactured from materials including, forexample, aluminum, steel, and/or any other suitable material. In oneexample, first support member 41 and second support member 43 mayinclude a military-grade aluminum material.

In addition to fastening points 50, each of first support member 41 andsecond support member 43 may also include an aperture 42 configured toreceive at least one object (e.g., restraints 4). Each aperture 42associated with first support member 41 and second support member 43 maybe configured to be substantially aligned upon assembly of first supportmember 41 and second support member 43, such that a substantiallysingular aperture may result. Therefore, each aperture 42 associatedwith first and second support members 41 and 43 may be of substantiallythe same size, shape, and location within first support member 41 andsecond support member 43. Further, each aperture 42 may be defined byone or more edges extending substantially parallel to the perimeter ofits associated support member (e.g., first support member 41 or secondsupport member 43). In one example, each aperture 42 may be of an ovalor oblong shape and may taper from a first end 46 to a blade end 48 offrame 44. One of skill in the art will recognize that aperture 42 may beof any desired size and shape and the examples described herein are notintended to be limiting.

Each aperture 42 may be configured to receive at least one object (e.g.,one or more restraints 4) within aperture 42. For example, free endsassociated with restraints 4 may be passed through aperture 42 and thefree end subsequently secured (e.g., to cargo 2). Because aperture 42may be fully enclosed, it may be desirable to maintain a free end of anobject such that the free end may be passed through aperture 42 andsecured. Alternatively, as shown in FIG. 6, another exemplary restraintrelease device 40 may include a hinged opening 52 allowing access toaperture 42. In such an exemplary restraint release device 40, firstsupport member 41 and second support member 43 may include a hingedfastening point 51 at first end 46 associated with frame 44. In additionto hinged fastening point 51, first support member 41 and second supportmember 43 may further include a hinged section 55 configured to pivotabout hinged fastening point 51 to allow creation of opening 52, andthus positioning of an object lacking a free end within aperture 42.Following positioning of an object within aperture 42, hinged section 55may be pivoted about hinged fastening point 51 and subsequently secured(e.g., with fasteners 49 and/or any other suitable connector) therebyclosing opening 52 to aperture 42.

Returning to FIGS. 5A and 5B, blades 45 and 47 may be configured tocause a cutting of an object (e.g., release of restraints 4). Blades 45and 47 may include a material conducive to creating a cutting surface(e.g., a sharp edge), including for example, steel or stainless steelthat has been sharpened or otherwise treated to provide a sharp edge.For example, blades 45 and 47 may be manufactured from a steel material,hardened, and honed using conventional methods for creating a singlebladed cutting surface. While blades 45 and 47 are described herein astwo separate pieces of material, it may be possible to combine blades 45and 47 such that a single piece of material comprises the cuttingsurfaces associated with blades 45 and 47.

Blades 45 and 47 may be opposably mounted at blade end 46 associatedwith frame 44 such that at least one cutting surface may be exposedwithin aperture 42. Exposure of at least one cutting surface may createan area conducive to cutting an object within aperture 42 when a forceis applied to frame 44. In one example, blades 45 and 47 may be mountedat an angle approximating a taper associated with aperture 42 such thatan acute angle (e.g., approximately 10 to 20 degrees) is formed betweenthe cutting surface of each of blades 45 and 47. One of ordinary skillin the art will recognize that other suitable acute angles andconfigurations associated with blades 45 and 47 may be utilized withoutdeparting from the scope of the present disclosure.

Blades 45 and 47 may further include one or more fastening points thatmay be substantially aligned with fastening points 50 associated withfirst support member 41 and second support member 43. Such aconfiguration may allow for a removable connection of blades 45 and 47to frame 44, and may, therefore, allow for interchanging (e.g.,replacement) of blades at desired intervals. In addition, one or morefastening points associated with blades 45 and 47 may include elongatedholes to allow for location adjustment of blades 45 and 47 in relationto fastening points 50 within aperture 42. Such a configuration may bedesirable to generate a desired cutting force on objects within aperture42, among other things.

INDUSTRIAL APPLICABILITY

The disclosed devices may be applicable to any parachute system. Thedisclosed devices may particularly applicable to cargo delivered viaairdrop from an aircraft to remote locations using a static parachutedeployment line. Because the disclosed devices may assist in reducingstresses associated with static line deployment of a parachuteassociated with cargo, damage, particularly to the parachute canopy, maybe reduced. Further, wear associated with a restraint release may alsobe reduced, while allowing for replacement of worn items associated withthe restraint release. Operation of the disclosed embodiments of thedevices will now be explained.

The following discussion presumes that a parachute suitable fordelivering cargo 2 from an altitude associated with an aircraft has beenpacked into parachute container 3, and that parachute container 3 hasbeen, or will be, affixed substantially in contact with cargo 2 usingrestraints 4 prior to deployment from an aircraft. It is also presumedthat cargo straps/risers or other suitable device (not shown) may beused to suspend cargo 2 from parachute (not shown) following deployment,as is known in the art.

FIG. 7 is an exemplary flowchart 700 illustrating a method fordeployment of an exemplary parachute and cargo system 1. Elementsassociated with parachute deployment line 8 may be operably connected toan aircraft at aircraft end 114 (e.g., via connector 14), parachutecontainer 3 at container loop 28, and parachute canopy (not shown) atcanopy loop 29 (step 705). Further, multi-ring release system 16 may beassembled and retaining pin 24 inserted through cord section 17, suchthat first ring 19 is retained, thereby retaining subsequent rings(e.g., second ring 20 and load ring 18).

Restraints 4 may then be placed within aperture 42 of restraint releasedevice 40 (step 710). A free end associated with restraints 4 may beplaced through aperture 42 and secured such that parachute container 3is substantially in contact with cargo 2 prior to exiting the aircraft.Alternatively, if restraints 4 have already been tied off or otherwisesecured to cargo 2, a hinged release device 40 (e.g., similar to thatshown in FIG. 6) may be used such that hinge section 55 may be opened,restraints 4 placed within aperture 42, and hinge section 55 closed toretain restraints 4.

Upon reaching a delivery location associated with cargo 2, parachute andcargo system 1 may be deployed from the aircraft (step 715). Forexample, parachute and cargo system 1 may be pushed or otherwise forcedto leave the inside of the aircraft.

Because segments of material associated with parachute deployment line 8may be of fixed length, as parachute and cargo system 1 descends awayfrom the aircraft, and because aircraft end 114 of parachute deploymentline 8 may be operably connected to the aircraft, pulling forces may beexerted on various components of parachute deployment line 8. Restraintrelease device 40 may receive a pulling force causing restraints 4 to bedrawn into the acute angle formed between blades 45 and 47, therebyresulting in contact with cutting surfaces. Such contact may then resultin a cutting (i.e., release) of restraints 4 (step 720). Subsequently, aforce exerted through parachute deployment line 8 to container loop 28may cause an opening of parachute container 3 and deployment ofparachute canopy (not shown) (step 725).

As parachute and cargo system 1 continue to descend away from theaircraft, the connection between canopy loop 29 and retaining pin 24 viathird length of material 26 may undergo a pulling force, which mayresult in the removal of retaining pin 24 from cord section 17 (step730). As described above, upon removal of retaining pin 24 from cordsection 17, each ring associated with multi-ring release section 16 maycascade loose, thereby releasing load ring 18 from multi-ring releasesystem 16. Such a release may then result in separation of first segmentof material 10 from second segment of material 12 and, therefore,breakaway of parachute release line 8.

Utilizing devices and methods of the present disclosure may result inreductions in force used for releasing restraints 4 and breaking awayparachute deployment line 8. For example, utilizing some exemplarydevices and methods of the present disclosure may result in a maximumbreakaway force of approximately 52 to 75 pounds. Further, someexemplary devices and methods of the present disclosure may result in amaximum restraint release force of approximately 28 to 32 pounds, whileminimizing damage to restraint release device 40.

Although the present invention herein has been described with referenceto particular embodiments, it is to be understood that these embodimentsare merely illustrative of the principles and applications of thepresent invention. It is therefore to be understood that numerousmodifications may be made to the illustrative embodiments and that otherarrangements may be devised without departing from the spirit and scopeof the present invention as defined by the appended claims.

1. A releasable deployment line for a parachute system, comprising: afirst segment of material comprising an aircraft end configured to beoperably connected to an aircraft, and a release end configured to beoperably connected to a first section of a multi-ring release system; asecond segment of material comprising a container end configured to beoperably connected to a parachute container, and a ring end configuredto be operably connected to a second section of the multi-ring releasesystem; and a third segment of material comprising a parachute endconfigured to be operably connected to a parachute within the parachutecontainer, and a pin end configured to be operably connected to aretaining pin associated with the first section of the multi-ringrelease system.
 2. The releasable deployment line of claim 1, furthercomprising the retaining pin, wherein the ring end and the release endare operably connected together by the slidable positioning of theretaining pin within a retaining loop associated with the multi-ringrelease system.
 3. The releasable deployment line of claim 1, furthercomprising the multi-ring release system, wherein the multi-ring releasesystem includes at least three rings.
 4. The releasable deployment lineof claim 1, wherein the first, second, and third segment of materialinclude at least one of a nylon webbing, a braided nylon, a polyesterwebbing, and a cotton webbing.
 5. The releasable deployment line ofclaim 1, wherein a thickness associated with the third segment ofmaterial is less than a thickness associated with the first or secondsegment of material.
 6. The releasable deployment line of claim 1,wherein the second segment of material is at least 4 times the length ofthe first segment of material.
 7. The releasable deployment line ofclaim 2, further comprising the retaining loop, wherein the multi-ringrelease system is configured to enable separation of the first segmentof material from the second segment of material upon removal of theretaining pin from the retaining loop.
 8. The releasable deployment lineof claim 1, wherein the third segment of material is slidably connectedto the second segment of material.
 9. The releasable deployment line ofclaim 8, wherein the third segment of material is configured to exert atension on the retaining pin following deployment of the parachute.